U.S. patent number 7,322,180 [Application Number 11/023,601] was granted by the patent office on 2008-01-29 for turbo-jet engine with fan integral with a drive shaft supported by first and second bearings.
This patent grant is currently assigned to Snecma Moteurs. Invention is credited to Gael Bouchy, Guy Lapergue, Regis Servant.
United States Patent |
7,322,180 |
Lapergue , et al. |
January 29, 2008 |
Turbo-jet engine with fan integral with a drive shaft supported by
first and second bearings
Abstract
A turbo-jet engine including a fixed structure and a fan rotor
mounted on a drive shaft supported by a first bearing and a second
bearing. The engine further comprises an axial retaining device
configured to form an emergency bearing and to cooperate with the
fixed structure and mounted rigidly to the drive shaft. The engine
includes a structural flange on which the second bearing is fixed,
and the axial retaining device comprises a retaining disk mounted
on the drive shaft and configured to cooperate with a stop disk of
the flange to axially retain the fan and form an emergency
bearing.
Inventors: |
Lapergue; Guy (Rubelles,
FR), Servant; Regis (Vigneux sur Seine,
FR), Bouchy; Gael (La Chapelle Iger, FR) |
Assignee: |
Snecma Moteurs (Paris,
FR)
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Family
ID: |
34684993 |
Appl.
No.: |
11/023,601 |
Filed: |
December 29, 2004 |
Prior Publication Data
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Document
Identifier |
Publication Date |
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US 20050172608 A1 |
Aug 11, 2005 |
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Foreign Application Priority Data
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Feb 6, 2004 [FR] |
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04 01145 |
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Current U.S.
Class: |
60/226.1;
415/104 |
Current CPC
Class: |
F01D
21/045 (20130101) |
Current International
Class: |
F02K
3/02 (20060101) |
Field of
Search: |
;60/791,226.1
;415/104,107,229 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
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1 013 896 |
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Jun 2000 |
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EP |
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2 752 024 |
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Feb 1998 |
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FR |
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Primary Examiner: Rodriguez; William H.
Attorney, Agent or Firm: Oblon, Spivak, McClelland, Maier
& Neustadt, P.C.
Claims
The invention claimed is:
1. A turbo-jet engine comprising: a fixed structure; a fan rotor
fixed to a drive shaft supported by a first bearing and a second
bearing; an axial retaining device configured to cooperate with the
fixed structure and mounted rigidly to the drive shaft; and a
structural flange on which the second bearing is fixed, wherein the
axial retaining device is configured to form an emergency bearing
and includes a retaining disk mounted on the drive shaft, the
retaining disk configured to cooperate with a stop disk on the
flange to axially retain the fan and further configured to
cooperate with a longitudinal sleeve of flange to form a bearing
surface.
2. The turbo-jet engine as recited in claim 1, wherein the axial
retaining device is arranged to transmit axial stresses directly to
the drive shaft.
3. The turbo-jet engine as recited in claim 2, wherein the second
bearing includes an inner ring, an outer ring and rollers mounted
between said inner and outer rings, the retaining disk includes
radial teeth axially bearing upon teeth of the drive shaft and
locked in rotation by longitudinal teeth of the inner ring of the
second bearing.
4. The turbo-jet engine as recited in claim 3, wherein the outer
ring has a radially exterior surface configured to mate with a
housing connected to the flange, and the radially exterior surface
and housing mate together as a ball joint.
5. The turbo-jet engine as recited in claim 1, wherein the axial
retaining device includes an upstream bearing surface, and the
structural flange includes a downstream bearing surface against
which downstream bearing surface the upstream bearing surface
slides in the event of a decoupling of the first bearing from the
fixed structure, and downstream is a direction taken traveling from
the first bearing toward the second bearing along an axis of the
turbo-jet engine, and upstream is a direction opposite the
downstream direction.
6. The turbo-jet engine recited in claim 5, wherein one of the
upstream and downstream bearing surfaces is spherical.
7. The turbo-jet engine recited in claim 5, wherein the retaining
disk is upstream of the second bearing.
8. The turbo-jet engine as recited in claim 1, wherein the
retaining disk includes a radial bearing surface configured to
slide against an interior annular surface of the flange while the
first bearing is in a state decoupled from the fixed structure.
9. The turbo-jet engine as recited in claim 8, wherein the
retaining disk includes an axial bearing surface configured to
slide against a conical surface of the flange while the first
bearing is in the state decoupled from the fixed structure.
10. The turbo-jet engine as recited in claim 1, further comprising
first shearing screws connecting the flange to the first bearing
via a first bearing support.
11. The turbo-jet engine as recited in claim 10, further comprising
second shearing screws connecting the second bearing to the flange
and which are configured to shear to allow the retaining disk to
make contact with the flange.
12. The turbo-jet engine as recited in claim 11, wherein the second
bearing includes rollers configured to permit axial movement of the
shaft relative to the fixed structure after the second shearing
screws break, but before the retaining disk makes contact with the
flange.
13. The turbo-jet engine as recited in claim 1, wherein the
retaining disk is mounted in an annular groove of the drive
shaft.
14. The turbo-jet engine as recited in claim 1, wherein the
retaining disk is mounted on the drive shaft downstream of the
flange when downstream is a direction taken traveling from the
first bearing toward the second bearing along an axis of the
turbo-jet engine.
Description
BACKGROUND OF THE INVENTION
1. Field of the Invention
The present invention pertains to the area of jet engines and more
particularly to engines whose fan is integral with a drive shaft
which is supported by a first bearing and a second bearing.
Said turbo-jet engine, from upstream to downstream in the direction
of the exhaust stream, comprises a fan, one or more compressor
stages, one or more turbine stages and an exhaust pipe. The fan
comprises a rotor provided with blades on its circumference which,
when caused to rotate, drive air into the turbo-jet engine. The fan
rotor is supported by the low pressure rotor shaft of the engine.
It is centred on the axis of the jet engine by a first bearing
which is upstream from a second bearing joined to the fixed
structure, to the intermediate casing in particular.
In the remainder of the description, insofar as the fan is mounted
integral with the compressor shaft, which is the shaft of the low
pressure rotor in a double-body engine, this shaft shall be
designated by the single term compressor shaft.
The first bearing is supported by a support piece forming an
enclosure around the compressor shaft, oriented downstream from the
first bearing and being attached to a fixed structure of the jet
engine. The second bearing is supported by a support piece that is
also attached to a fixed structure of the jet engine.
It may happen that a fan blade is accidentally lost. The result is
substantial imbalance on the compressor shaft which leads to loads
and vibrations on the bearings, transmitted via their support
pieces to the fixed structures of the jet engine which may
therefore be damaged.
2. Description of the Related Art
To prevent the risk of too extensive damage to the jet engine, the
structure may be over-dimensioned or, as proposed by patent FR 2
752 024, an uncoupling system for the first bearing may be
provided. The support piece of the first bearing is attached to the
structure of the jet engine by so-called shearing screws which
contain a weakened portion causing their rupture if the loads
applied are too high. Therefore, when an imbalance occurs on the
compressor shaft, the stresses induced on the first bearing are
transmitted to the shearing screws which break, uncoupling the
support piece of the first bearing from the structure of the jet
engine. According to one embodiment, the support of the second
bearing is associated with the support of the first bearing,
accompanying it in the event of uncoupling. The stresses caused by
the imbalance are then no longer transmitted to the fixed structure
of the jet engine by these support pieces.
However, after uncoupling of the bearings, the fan continues to
rotate and it is possible that the compressor shaft is no longer
able to rotate about its axis undergoing major displacement which
may damage the fixed structure of the jet engine. Patent FR 2 752
024 provides in this case, on the fixed structure of the jet
engine, for a ridge surrounding the support piece of the two
bearings and acting as axial stop and as emergency bearing.
However, in this case, the emergency bearing is radially far
distant from the original bearings, which completely modifies the
distribution of stresses on the various engine parts.
Finally, since the second bearing is able, in some cases, to ensure
the maintaining of the compressor shaft after uncoupling of the
first bearing, it is not necessary for both bearings to be
systematically uncoupled simultaneously, as it is always preferable
to maintain the jet engine in configurations that are the closest
to normal.
SUMMARY OF THE INVENTION
The present invention sets out to overcome these disadvantages.
For this purpose, the invention concerns a turbo-jet engine
comprising a fixed structure, a fan rotor integral with a drive
shaft supported by a first bearing and a second bearing,
characterized in that it includes means forming axial retaining
means for the fan rotor and/or forming an emergency bearing,
cooperating with means of the fixed structure and mounted integral
with the drive shaft.
Preferably, since the jet engine comprises a structural flange on
which the second bearing is fixed, the means forming axial
retaining means for the fan and/or forming an emergency bearing
comprise a retaining disk mounted on the drive shaft and
cooperating with a stop disk of the flange for axially retaining
the fan, and a longitudinal sleeve of the flange to form an
emergency bearing.
Further preferably, the means forming the axial retaining of the
fan and/or an emergency bearing are arranged to transmit axial
stresses directly to the drive shaft. If this were not the case, at
the time of axial retaining of the fan, the stresses generated on
the support pieces of the bearings could propagate along the
support piece of the second bearing and lead to rupture of the lock
nut of the second bearing on the compressor shaft. Such rupture
would cancel out the axial retaining of the second bearing on the
compressor shaft. As the fan would continue to rotate, it would
drive the compressor shaft forwardly which could slide in the
second bearing that is not axially retained, and onto the other
elements fitted at this point. The result would be the expelling of
the fan outside the jet engine whose consequences would be
disastrous.
Advantageously, the second bearing comprises an inner ring, an
outer ring and rollers mounted between said rings, the retaining
disk comprises radial teeth bearing axially upon the teeth of the
drive shaft and locked in rotation by longitudinal teeth of the
inner ring of the second bearing.
BRIEF DESCRIPTION OF THE DRAWINGS
The invention will be more readily understood through the following
description of a preferred embodiment of the turbo-jet engine of
the invention, with reference to the appended drawings in
which:
FIG. 1 shows an axial section profile view of the preferred
embodiment of the invention,
FIG. 2 is an enlarged view of the area in FIG. 1 contained within
space C;
FIG. 3 is a perspective rear view of the compressor shaft and
structural flange of the preferred embodiment of the invention,
FIG. 4 is an exploded, perspective, rear view of the compressor
shaft, the structural flange and retaining ring in the preferred
embodiment of the invention,
FIG. 5 is an exploded, perspective, rear view of the compressor
shaft, the structural flange, retaining ring and inner ring of the
second bearing in the preferred embodiment of the invention,
FIG. 6 is an exploded, perspective, rear view of the compressor
shaft, structural flange, retaining ring, inner ring of the second
bearing and the support for the second bearing in the preferred
embodiment of the invention,
FIG. 7 is a schematic perspective view of the mounting of the outer
ring in the support of the second bearing in the preferred
embodiment of the invention,
FIG. 8 is a perspective view of the structural flange in the
preferred embodiment of the invention,
FIG. 9 is schematic side section view of the second bearing in the
preferred embodiment of the invention, after rupture of the
compressor shaft, and
FIG. 10 shows a section view of another embodiment of the
invention.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS
With reference to FIG. 1, the turbo-jet engine of the invention
comprises a fan 2, whose rotor has blades 3 extending radially
around the axis 4 of the jet engine. The fan shaft 2 is fixed,
downstream from blades 3, to the compressor shaft 5 of globally
cylindrical shape. This is the low pressure compressor shaft. In
the remainder of this description the assembly of the fan shaft 2
and compressor shaft 5 shall be referred to as the compressor shaft
5 or drive shaft 5. The compressor shaft is supported by a first
bearing 6 and a second bearing 7 located downstream of the first
bearing 6.
With reference to FIG. 2, the first bearing comprises an inner ring
8 and an outer ring 9, between which ball-bearings 10 are mounted.
The inner ring 8 is mounted integral with the compressor shaft 5
and the outer ring integral with a bearing support piece 11, called
hereinafter first bearing support 11. The ball-bearings 10 allow
rotation of the inner ring 8, and hence of the compressor shaft 5,
with respect to the outer ring 9, and hence with respect to the
first bearing support 11.
The first bearing support 11 extends from the first bearing 6 in
downstream direction; it is of globally cylindrical shape, slightly
conical, its diameter increasing in downstream direction. It is
mounted on a flange 18 of the fixed structure of the jet engine 1,
integral in particular with the intermediate casing of the engine,
and hereinafter called structural flange 18, by means of a
downstream clamp 12 in which shearing screws 13 are screwed. These
shearing screws 13 comprise a weakened portion 13' having low
resistance to traction forces leading to their rupture when
stresses become too high, in particular when an imbalance occurs on
the compressor shaft 5 subsequent to loss of a blade 3 in
particular.
The second bearing 7 comprises an inner ring 14 and an outer ring
15, between which rollers 16 are mounted. The inner ring 14 is
mounted integral with the compressor shaft 5, and the outer ring 15
is mounted integral with the fixed structure of the jet engine 1
when in normal operation, as will be described below. The rollers
16 are mounted parallel to the axis 4 of the jet engine 1, in a
channel 14a extending around the circumference of the inner ring
14, and are held distant from one another by a retainer 17 well
known to persons skilled in the art. They allow rotation of the
inner ring 14 with respect to the outer ring 15, and thereby of the
compressor shaft 5 with respect to the fixed structure of the jet
engine 1.
The second bearing 7 is supported by a bearing support piece 19,
hereinafter called second bearing support 19, comprising a housing
20, or ring 20, which tightly surrounds the outer ring 15 of the
second bearing 7, on whose circumference a fixation clamp 21
extends radially, screwed to the structural flange 18 by shearing
screws 22.
The outer ring 15 of the second bearing 7 comprises an outer
surface 23 of convex spherical shape when viewed in axial section.
This convex spherical surface 23 fits onto the inner surface 24 of
ring 20 of the second bearing support 19, of concave spherical
shape. The two spherical surfaces, convex 23 and concave 24,
between them form a connection forming a ball-joint (23, 24). They
are arranged so that under normal operation of the jet engine 1,
the connection forming a ball joint (23, 24) does not rotate. The
outer ring 15 of the second bearing 7 is then fixed with respect to
the second bearing support 19 and hence with respect to the fixed
parts of the jet engine 1. Its behavior in the event of loss of a
blade 3 is described further on.
The description of the structure of the elements of jet engine 1 in
the region of the second bearing 7 will be made by describing the
mounting of its elements, with reference to FIGS. 3 to 6, which
will contribute towards the understanding of their arrangement.
With reference to FIG. 3, the compressor shaft 5, above the
structural flange 18, comprises two projecting annular portions,
upstream 25 and downstream 26, forming an annular groove 27.
Projecting portion 26 comprises radial notches 26', thereby forming
teeth 26'' between them. Teeth 26'' and notches 26' are preferably
of equal circumferential size and therefore, overall, each extend
over one half of the circumference of the compressor shaft 5.
With reference to FIG. 4, a retaining disk 28 is mounted in the
annular groove 27 of the compressor shaft 5. This retaining disk
28, on its inner radial edge, comprises notches 28' and radial
teeth 28'' whose circumferential dimensions correspond to those of
notches 26' and teeth 26'' of compressor shaft 5. On mounting, the
retaining disk 28 is fitted onto the compressor shaft 5 in upstream
direction, its teeth 28'' are inserted into notches 26' of the
compressor shaft 5 until they abut the downstream surface of the
upstream projecting annular portion 25 of compressor shaft 5; the
retaining disk 28 is then rotated about axis 4 of the jet engine 1
until its teeth 28'' are axially aligned with the teeth of the
compressor shaft 5; in this position they are hemmed between the
downstream surface of the upstream projecting annular portion 25
and the upstream surface of teeth 26'' of compressor shaft 5,
whilst the notches 26', 28' of the compressor shaft 5 and of
retaining disk 28 are axially aligned.
With reference to FIG. 5, the inner ring 14 of the second bearing
7, on its upstream portion, comprises notches 14' and longitudinal
teeth 14'', whose circumferential dimensions correspond to the
circumferential dimensions of notches 26', 28' and of teeth 26'',
28'' previously described. The inner ring 14 is fitted onto the
compressor shaft 5 and its teeth 14'' are inserted in notches 26',
28' of compressor shaft 5 and of retaining disk 28 until they abut
the downstream surface of the upstream projecting annular portion
25 of the compressor shaft 5, the transverse surface of its notches
14' then abutting teeth 26'' of the compressor shaft 5. Therefore,
the teeth 14'' of the inner ring 14 lock the retaining disk 28 in
rotation, whose teeth 28'''' axially abut the teeth 26'' of the
compressor shaft 5.
With reference to FIG. 6, the rollers 16 are mounted on the inner
ring 14, in channel 14a provided for this purpose; the retainer 17
holding them together is not shown. The outer ring 15 of the second
bearing 7, mounted in the second bearing support 19, is fitted
around rollers 16; the inner surface 15a of the outer ring 15 is
rectilinear, from an axial section viewpoint, having a greater
longitudinal dimension than rollers 16. The clamp 21 of the second
bearing support 19 is fixed to the structural flange 18 via
shearing screws 22.
The mounting of the outer ring 15 of the second bearing 7 in the
ring 20 of the second bearing support 19, so as to form the
connection forming a ball joint (23, 24), will now be explained
with reference to FIG. 7. The ring 20 of the second bearing support
19 comprises two mounting notches 20', 20'', that are diametrically
opposite, whose circumferential dimension corresponds to the
longitudinal dimension of outer ring 15 of the second bearing 7.
The outer ring 15 is shown on the side facing the second bearing 19
and is slipped into these notches 20', 20''. It is then rotated
90.degree. so that its outer surface 23 bears upon the inner
surface 24 of ring 20 of the second bearing support 19, thereby
forming a connection forming a ball joint (23, 24).
Other elements may be fitted onto the compressor shaft 5 downstream
from inner ring 14 of the second bearing 7. For example, in this
case, with reference to FIGS. 1 and 2, a movement capturing device
29 is provided to drive other elements by means of the movement of
compressor shaft 5, together with a so-called labyrinth joint 30.
Once all the elements have been fitted, the assembly is axially
locked by a lock nut 31.
With reference to FIG. 8, the structural flange 18 is bored in its
centre. In its central part, it comprises a longitudinal sleeve 32,
at whose upstream end a stop disk 33 extends continuously and
radially inwards, whose inner edge forms the central bore of flange
18. The stop disk 33 is arranged so that the upstream surface 34 of
the retaining disk 28 is able to bear upon its downstream surface
35. The bearing surfaces 34, 35 formed by these two surfaces 34, 35
are arranged complementary fashion so that the bearing of one on
the other is as homogeneous as possible. In the embodiment
described herein of turbo-jet engine 1 of the invention, the
bearing surfaces 34, 35 are of conical shape. These bearing
surfaces could also be planar, or advantageously spherical. The
function of the stop disk 33 is to axially block the compressor
shaft 5 in the event of rupture, so that the fan 2 that is integral
therewith is not driven forwardly as will be explained below.
The functioning of the turbo-jet engine 1 of the invention in the
event of loss of a blade 3 of fan 2 will now be described in more
detail.
The loss of a blade 3 causes an imbalance on the compressor shaft
5. The induced stresses cause rupture of the shearing screws 13
fixing the first bearing support 11 to the structural flange 18,
and the uncoupling of this support 11 from the fixed structure of
the jet engine 1.
The second bearing 7 is subsequently not necessarily uncoupled from
the fixed structure of the jet engine 1, the connection forming a
ball joint (23, 24) making it possible to absorb some flexion of
the compressor shaft 5. We have seen that adjustment of the outer
ring 15 of the second bearing 7 in the ring 20 of the second
bearing support 19 is made so that the connection forming a ball
joint (23, 24) does not rotate under normal operation of the jet
engine 1, but is able to rotate in the event of imbalance on the
compressor shaft 5. Therefore, flexion of the compressor shaft 5
causes rotation of the connection forming a ball joint (23, 24)
about the centre of the sphere defined by the spherical surfaces
23, 24 forming this sphere.
Should the flexion of compressor shaft 5 be too extensive, however,
or should this flexion not be absorbable by simple rotation of the
connection forming a ball joint (23, 24) in particular if flexion
is off-centred with respect to axis 4 of the jet engine 1, the
shearing screws 22 fixing the second bearing support 19 to the
structural flange 18 will break. This rupture enables radial
movement of the second bearing 7 and of its support 19. In
addition, longitudinal movements are allowed by axial sliding of
rollers 16 on the inner surface 15a of outer ring 15 of the second
bearing 7, whose longitudinal dimension is greater than that of the
rollers 16.
Therefore, through the invention, the uncoupling kinematics of the
first bearing 6 are tolerated at the second bearing 7 without
causing the onset of excess stresses on rollers 16, since radial,
longitudinal and angular movements are permitted at the second
bearing 7. The movements of the parts are not hindered.
Should rollers 16 break, however, the retaining disk 28, via its
radial outer surface 36, is able to abut the inner surface 37 of
the longitudinal sleeve 32 of flange 18; these then act as
emergency bearing. Should this function be required for disk 28 and
sleeve 32, the radial distance between the outer surface 36 of the
retaining disk 28 and inner surface 37 of the longitudinal sleeve
32 may be sized accordingly.
Rupture of the compressor shaft 5 may, however, occur despite the
various safety devices described above. An ultimate safety system
is therefore provided. In the event of rupture of the compressor
shaft 5, the rotation of fan 2 drives the fan forwardly with the
compressor shaft 5 with which it is integral. The upstream surface
34 of the retaining disk 28 then comes to abut the downstream
surface 35 of the stop disk 33, integral with the fixed structure
of the jet engine 1. The stop disk 33 therefore acts as axial stop
for the fan 2 in the event of rupture of the compressor shaft 5 (or
of the turbine shaft with which the compressor shaft 5 is
integral). The advantage of a spherical shape for the two bearing
surfaces 34, 35 of retaining disk 28 and of stop disk 33
respectively becomes clearly apparent here; it enables homogeneous
contact irrespective of the incline of the compressor shaft 5 with
respect to the structural flange at the time of contact.
On and after contact, the stresses are transmitted by the retaining
disk 28 to its teeth 28'' which transmit the same to teeth 26'' of
compressor shaft 5 and hence to the compressor shaft 5. Therefore,
through the arrangement of the retaining disk 28 and of inner ring
14 of the second bearing 7 on the compressor shaft 5, the stresses
caused by axial retaining of fan 2 by stop disk 33 are not
transmitted to the lock nut 31, a transmission which would have
disastrous consequences since rupture of the lock nut 31 would lead
to the sliding of the various elements fitted around the compressor
shaft 5 and the forward expelling of fan 2 and of compressor shaft
5; on the contrary, however, these stresses are transmitted to the
compressor shaft 5.
With the device of the invention it is therefore possible to ensure
axial retaining of the compressor shaft, and hence of fan 2 at the
second bearing 7 with no transmission of any retaining stresses to
the lock nut 31 of the second bearing 7.
The emergency bearing device and the axial retaining of the jet
engine according to the invention have been described in
combination with the connection forming a ball joint (23, 24) since
their functions are complementary.
Evidently, the device of the invention, with its retaining disk 28
and stop disk 33, arranged so that their contact stresses are not
transmitted to the lock nut 31 but directly to the compressor shaft
5, may be applied to any type of jet engine comprising a compressor
shaft 5 supported by two bearings 6,7 irrespective of the type of
these two bearings 6,7.
For example, in FIG. 10, a turbo-jet engine 41 can be seen that is
practically similar to the jet engine 1 previously described. In
particular it comprises a drive shaft 45 supported by a first
bearing 46 and a second bearing 47. The first bearing 46 is
supported by a support piece 411 attached to a flange 418, similar
to flange 18 previously described. The flange 418, in its central
part, also comprises a longitudinal sleeve 432 at whose upstream
end is a stop disk 433 extending continually and radially inwards,
whose inner edge forms the central bore of flange 418.
The second bearing 47 comprises an inner ring 414 similar to inner
ring 14 described above, and an outer ring 415 between which
rollers 416 are mounted. The outer ring 415, on its outer
circumference, comprises a fixation clamp 421 fixed to flange 418.
A retaining disk 428 similar to retaining disk 28 described above
is mounted on the drive shaft 45 in similar manner.
The retaining disk 428 here is arranged so that the radial distance
between its outer surface 436 and the inner surface 437 of the
longitudinal sleeve 432 is fairly short, so that the emergency
bearing function of the retaining disk 428 and of the longitudinal
sleeve 432 can be properly ensured. Therefore, should rollers 416
break, the outer surface 436 of the retaining disk 428 will come to
abut the inner surface 437 of the longitudinal sleeve 432 to
fulfill its function as emergency bearing, without radial
displacement being too extensive.
As before, in the event of rupture of the compressor shaft 45, the
upstream surface 434 of the retaining disk 428 comes to abut the
downstream surface 435 of the stop disk 433, which acts as axial
stop for the fan in the event of rupture of the compressor shaft
45. As before, the two bearing surfaces involved 434, 435 may be
planar, transverse, conical or spherical.
* * * * *